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Electrical architecture of an aircraft

An electrical architecture, aircraft technology, applied in electrical components, aircraft parts, aircraft indicating devices, etc., can solve problems such as deteriorating airborne mass balance

Pending Publication Date: 2022-01-04
THALES SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Furthermore, pooling requires additional systems such as contactor arrays, which worsens the onboard mass balance

Method used

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  • Electrical architecture of an aircraft
  • Electrical architecture of an aircraft
  • Electrical architecture of an aircraft

Examples

Experimental program
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Embodiment Construction

[0055] For the sake of clarity, the same elements will have the same reference numbers in the various figures.

[0056] figure 1 An example of an electrical architecture according to the invention is shown. figure 1 The electrical architecture of a twin-engine commercial aircraft is shown. Each of the propulsion engines M1 and M2 drives two generators: G1.1 and G1.2 for engine M1 and G2.1 and G2.2 for engine M2. The invention can be implemented regardless of the number of propulsion engines and regardless of the number of generators per engine. The invention can be implemented for other types of aircraft and for example for rotorcraft.

[0057] In the example shown, there are other generators in the aircraft, such as generator G3 driven by the APU and RAT. These auxiliary (APU) and backup (RAT) generators are not mandatory in the present invention, as will be seen further below. The electrical architecture includes the electrical distribution system EPDS that receives ele...

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PUM

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Abstract

The invention relates to an electrical architecture of an aircraft comprising: a plurality of primary generators (GEN1, GEN2) each associated with a propulsion engine of the aircraft; a plurality of primary electrical networks (AC1, AC2, essential AC) each associated with a primary generator in nominal operating mode; a single-part secondary electrical network (RES); an electrical energy accumulation device (BAT-HVDC) connected directly to the secondary network; a first electrical energy converter (CP1) arranged between the secondary electrical network and a first of the primary electrical networks, allowing energy to be transferred from the first of the primary electrical networks to the secondary electrical network, the first electrical energy converter (CP1) being intended to supply electrical energy to the electrical energy accumulation device in nominal operating mode; a second electrical energy converter (CP2) arranged between the secondary electrical network and a second of the primary electrical networks, allowing energy to be transferred from the secondary electrical network to the second of the primary electrical networks.

Description

technical field [0001] The present invention relates to improving the electrical architecture of aircraft. On commercial aircraft, electrical power is typically generated by a main generator mechanically coupled to the aircraft's propulsion engines. Each generator supplies an alternating current (AC) voltage, which is supplied to the electrical grid of the aircraft, which distributes the AC or direct current (DC) electrical energy required to operate the electrical loads located in the fuselage and engine regions. Background technique [0002] Traditionally, electricity with fixed frequency AC current (traditionally at 400 Hz) can be generated on commercial aircraft based on gas turbines rotating at variable speeds. The nominal voltage of the onboard AC network is usually 115V. On some modern aircraft this voltage has been increased to 230V. To achieve this, a speed control system is installed between the shaft of the gas turbine and the alternator, which can then rotate ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02J3/02H02J3/06H02J5/00
CPCH02J3/38H02M7/04H02J3/02H02J3/06H02J5/00B64D2221/00H02J2310/44H02J4/00B64D41/00B64D45/00H02J1/102H02J7/34Y02T50/50B64C25/405
Inventor J·德沃图尔
Owner THALES SA
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